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Hydrodynamic stability of rockets with headwall injection
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Image of FIG. 1.
FIG. 1.

Sketch of the rotational full-length rocket model permitting mass addition along both sidewall and headwall boundaries.

Image of FIG. 2.
FIG. 2.

Iso- factors for and . Results are shown in (a) through (d) for ,1,2,3.

Image of FIG. 3.
FIG. 3.

Neutral curves for different values of at and .

Image of FIG. 4.
FIG. 4.

Using and , we present the neutral curves for (a) simulated SRM with headwall burning and (b) simulated hybrid rocket engine. In (c), the effect of Reynolds number on the spatial shift in stability is illustrated for a simulated SRM with headwall burning ( and ). For the same case, the behavior of the streamwise wave number is plotted in (d) over a wide range of Reynolds numbers and fixed values of and .

Image of FIG. 5.
FIG. 5.

Spectrum of pressure amplitudes versus frequencies along a circular radius of and increasing distance from the headwall. Note the presence of large bumps in the pressure (and similarly in the unsteady radial and streamwise velocities) over a range of undesirable frequencies. As usual, we use to mimic inviscid behavior, for a hybrid rocket model, and for the most unstable scenario.

Image of FIG. 6.
FIG. 6.

Same as previous except for corresponding to a solid rocket model with reactive headwall.


Generic image for table
Table I.

Eigenvalues of the Taylor-Culick profile at , , , and .


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Scitation: Hydrodynamic stability of rockets with headwall injection